Multistage reaction toy



Dec. 29, 1970 R, F* P|PP|N, JR l 3,550,313

MULTISTAGE REACTION TOY Filed OCT.. 24, 1965 2 Sheets-Sheet l INVENTOR REGINALD F. PIPPIN ,JR

Dec. 29, 1970 R. F. PIPPIN, JR

MULTISTAGE REACTION TOY I 2 Sheets-Sheet 2 Filed OCT.. 24, 1965 62| ewb" FIG. 6

R. |.v wm DI MP El vP. NF D L A W.. G E Dn FIG. 7

United States Patent() 3,550,313 MULTISTAGE REACTION TOY Reginald F. Pippin, Jr., 7806 Ruxway Road, Towson, Md. 21204 Filed Oct. 24, `1965, Ser. No. 504,300 Int. Cl. A63h 27/ 00 U.S. Cl. 46-74 28 Claims ABSTRACT F THE DISCLOSURE A fluid discharge reaction-propelled toy missile with multiple stages releasably interconnected lby pressurizable, collapsibly flexible gripping wall sections, illustrated as pressure-expandable convex hollow bulbous gripping sections each resiliently releasably directly gripping a respective succeeding stage fluid discharge propulsion orifice and releasably sealing it from fluid discharge communication with the atmosphere. Self-sealing lateral inlet valves provided in individual stages enable separate individual stage pressurization from an external pressure source. Missiles are launched from a fluid-pressurizable ground-launching pad having a similar releasable missile-holding connection, with launch simulation enhancement provided by controlled-release lateral liquid spray orifices and a sprayenhancing annular deflector ring.

This invention relates to a reaction toy arrangement and method, and more particularly to a fluid expulsion type reaction motor missile arrangement.

It is a feature of this invention to provide a multistage reaction motor missile in which the stages are interconnected by a simple fluid-pressure-responsive connection and seal incorporating a laterally flexible diaphragm wall male connector on one stage and releasably fitting within the fluid discharge propulsion orifice of the next'succeeding stage to provide for pressure-responsive interstage securing and release and to effectively seal the fluid discharge propulsion orice of the next succeeding stage against effective fluid propulsion discharge until pressurereduction interconnection release is effected by the laterally flexible diaphragm wall male connector.

A further feature relates to the provision of a fluid discharge propelled multiple unit toy missile arrangement incorporating a laterally flexible gripping diaphragm wall male connector on one unit and releasably engageable in retentive holding and fluid-dischargesealing relation within the discharge orifice of a next succeeding stage unit through internal fluid pressurization of the male connector diaphragm wall while in place within such discharge orifice. Still a further feature relates to such an arrangement in which the laterally flexible gripping diaphragm wall male connector is longitudinally braced by internal bracing effectively connected thereto at spaced longitudinal positions therealong, while enabling lateral flexing of the diaphragm wall in response to differential lateral pressure thereon.

Still other objects, features and attendantadvantages will become apparent to one skilled in the art from`a reading of the following detailed description of several physical embodiments constructed in accordance 'with the invention, taken in conjunction with the accompanying drawings wherein: s

FIG. l is a longitudinal section view of a multistage rocket toy according to the invention,

FIG. 2 is a longitudinal section view of a rocket stage modified for ease of molding manufacture,

FIG. 3 is a fragmentary view` of a modified launcher and rocket arrangement, t v

ICC

FIG. 4 is a longitudinal section view of a further modified first stage rocket section,

FIG. 5 is a longitudinal section view of an additional modified first stage rocket section,

FIG. 6 is a fragmentary longitudinal section view of a modified fluid-pressure-responsive bulb connector-seal arrangement,

FIG. 7 is a section view taken on line 7-7 of FIG. 6,

FIG. 8 is a section view taken on line 8-8 of FIG. 6,

FIG. 9 is a fragmentary longitudinal section view of a further connector-seal arrangement modification.

Referring now to the figures of the drawings, in FIG. 1 is shown a multistage rocket toy 10 which in the present embodiment incorporates three stages, although it Will become apparent that with the present invention the number of stages is virtually unlimited within the propulsion capabilities of the given rocket size. The illustrative rocket 10 includes three self-separable stages 11, 21, 31, the lowermost or first stage 11 being releasably mounted on a launching pad 41 having a remote control pressure release launch-control valve 53 connected thereto through a hollow conduit 51.

Each separable stage or section 11, 21, and 31 includes a cylindrical body having a pressurizable liquid storage chamber 14, 24 and 34 respectively, enclosed by an annular side wall 13, 23, 33 respectively, and front and rear end walls 15, 16; 25, 26; and 35, 36, respectively. Stabilizing fins 19, 29, 39 are formed or secured on the outer surface of the respective stage sections 11, 21 and 31, and the final or upper stage 31 has a tapered or ogive shaped end 36 for decrease of air resistance during flight.

The forward end walls 16 and 26 of the first and second or penultimate stage sections 11 and 21 have a pressure-sensitive laterally flexible diaphragm wall male connector-seal in the illustrative form of a bulbous flexible nose protrusion 17, 27, respectively, which is as a function of pressure in the respective liquid storage chamber 14, 24, pressurizable for rigidizing thereof and depressurizable for ease of flexing and discharge thereof from a respective female connection 25a, 25b, 25C; and 35a, 35b, 35C in the adjoining next forward stage 21 and 31 respectively. Each bulbous nose protrusion 17, 27, includes a unitary relatively thin-walled integral diaphragm-like body structure having an intermediate enlarged annulus portion disposed between a smaller tip protrusion and a smaller annular portion adjacent the root end. The bulbous nose protrusions serve as pressure-responsive connector seals which lockingly engage and seal the respective female connecting and fluid discharge or expulsion openings 25a, 25b, 25C; and 35a, 35b, 35C. In the illustrative embodiment, each female connecting and fluid discharge or expulsion opening includes an intermediate annular groove portion 25a, 35a disposed between a relatively smaller diameter liquid discharge metering orifice `25b, 35h and a reduced `diameter smoothly rounded rim portion 25C, 35C. The flexible bulb connector-seals 17, 27 arepreferably shaped to be generally complementary to the respective mating female openings, although it will be appreciated that differences in shape and size may be accommodated to a degree dependent upon the elasticity of the material forming the bulbc0nnector seals, in which event when the seal integrity and connection strength are effectively maintained the effective pressurized joint is therefore formed of effectively substantially complementary relation. Some degree of pressure-responsive distension is present in all materials, and the extent of distension employed, if any, will depend upon the extent of manufacturing or design mismating and the elastic distension capabilities of the material forming the bulb protrusions.

As used herein, the term bulbous or bulb as applied to pressurizable laterally iiexible wall connector elements 17, 27, etc., is used in both the specific shape sense of a male shaped connector having an enlarged mid-section, and the generic action sense of a male shaped connector member generally which is capable of lateral swelling, and in each instance having an internal pressure responsive laterally fiexible wall section which is pressurizable when in place within a fluid discharge orifice t afford pressure responsively releasable holding action therewith. The fiuid-pressure-responsive laterally flexible diaphragm wall connector elements or members 17, 27, etc., may, of course, be formed with other configurations and constructions than the illustrated and preferred bulbous configurations and constructions.

Launching pad 41 is presure-respondsively connected to the female connecting and fluid discharge openings a, 15b, 15C of the first stage section 11 through the medium of a flexible bulb connector-seal 47 similar to interstage flexible bulb connector-seals 17 and 27.

Although the pressurizing of the various chambers 14, 24, 34 and 45 will tend to properly seat the pre-inserted bulb connector-seals in their respective female openings it may be advantageous and desirable in some instances, particularly in the ease of highly fiexible bulb connectorseal embodiments to employ a connector bulb insertion aid 71 which may take the form of a rod 73 having a handle 75. The rod 71 may be inserted through the female fluid discharge opening 15b, 25b of a particular rocket section to push on and effect manipulation of the respective bulb connection-seal 17 or 27 into its corresponding adjoining next stage complementary female opening a, 25b, 25e or 35a, 35b, 35e as the case may be. To enable use of insertion aid 71 with the interconnection between launcher pad 41 and the first stage section 11, the bottom wall 44 of pad 41 may be provided with a central removable plug 49 aligned with bulb connector-seal 47. Plug 49 may be formed with a double tapered module detent 49a for ease of insertion and removal and a recessed flat head 49b.

The rocket stage sections 11, 21 and 31 and launching pad 41 are each provided with a self-closing valve opening 13a, 23a, 33a and 43a, respectively, to enable pressurizing of the respective chambers 14, 24, 34 and 45, after assembly of respective adjoining stages, although the launch pad chamber 45 may if desired be pressurized through valve 53 and conduit 51. Each of the self-closing valves includes pressure-responsive self-obturating inner closure lips 13b, 23b, 33b, and 43b respectively and a flared outer guide opening as indicated at 13e may also be provided if desired. For purposes of illustration of differing locations for the valves, each of the valves 13a, 23a, 33a is shown at a different location on its respective rocket stage section, although it will be appreciated that for a given assembly all valve openings 13a, 23a and 33d would normally lie in the same general position on the respective different stage sections. A conventional valve needle 61 of the type commonly employed for inflating footballs, basketballs, etc., and a conventional air pump (not shown) may be used in conjunction with valve openings 13a, 23a, 33a, and 43a to effect pressurizing of the respective chambers 14, 24, 34 and 45.

It will be appreciated that inasmuch as the illustrated first and second stages 11 and 21 are interchangeable, it is a simple matter to reduce the number of stages to two or one by elimination of one or both of stages 11 and 21, and to increase the number of stages as desired by adding additional stages identical to either stage 11 or 21.

As an example of assembly and launching of the rocket 10, Water is added to partially fill first stage storage chamber 14 as by pouring into the effective funnel-mouthed opening 15a, 15b, 15e` while the section 11 is inverted, and launching pad 41 is thereupon mated with section 11. While retaining the assembly 11, 4l in inverted position the chamber 45 is pressurized through valve opening 43a or through line 51 to effect secure 'retaining connection and sealing of the launching pad 41 to the first stage 11 through pressure-responsive bulb and socket connection `47, 15a, 15b, 15C. Thereupon, =water is added to partially fill storage chamber 24 in second stage section 21 while holding the second stage in inverted position, and the first stage bulb connector-seal is then inserted into the openings 25a, 25h, 25C, after which the first stage chamber 14 is pressurized through valve opening 13a to lock section 21 to first stage section 11 and the assembly 11, 41. This same operation is then repeated for partial filling of third stage section 31, connection thereof to second stage section 21, and subsequent pressurizing of second stage 21 through valve opening 23a to lock sections 21 and 31 together. The assembly operation is then completed by pressurizing final stage chamber 34 through valve opening 33a, and the assembly is then ready for launch.

The foregoing method of assembly is most advantageous when the bulb connector-seals 17 et al. are of sufficient rigidity to enable fieXing insertion without the aid of tool 71, as only two pieces need be held together at a time in unsecured connected condition. However when it is necessary or desired to employ the insertion aid tool 71 on all interstage connections, a different assembly procedure may be employed. In this instance the final stage section 31 is first partially filled with water while inverted and thereupon the second stage section 21 is connected thereto by inserting the bulb connector-seal 27 into the openings 35a, 35b, 35C, using the tool 71 through second stage openings 25a, 25b, 25C to aid in this assembly. Water is then added through openings 25a, 25h, 25e to partially fill second stage 21, and first stage 11 is connected to stage 21 through insertion of bulb connector-seal 17 into openings 25a, 25h, 25C, using tool 71 through openings 15a, 15b, 15C. Water is then added to partially fill the storage chamber 14 of the first stage 11 while continuing to hold the assemblies 11, 21, 31 in inverted vertical position, and the launch pad 41 is then connected by removing the plug 49 and manipulating the tool through opening 46 to aid in positioning the bulb connector-seal within the mating connecting and fiuid discharge openings 15a, 15b, 15C of the first stage section 11. yPlug 49 is then replaced, and thereupon launching pad chamber `44 is pressurized through either valve opening 43 or conduit 51 and valve 53. This secures first stage 11 and launch pad 41 together in sealed relation and charnber 14 is thereupon pressurized through valve opening 13a to secure stages 11 and 21 together, whereupon second stage 21 is then pressurized through valve opening 23a to lock and seal stages 21 and 31 together, and nal stage chamber 34 is then pressurized through valve opening 33e to ready the assembly for launching. It will be appreciated that in this last described `method of assembly a holding jig or fixture may be used if desired to retain the various sections in position during assembly, although such may be accomplished by hand only if desired, particularly with the aid of a second person.

To launch the rocket 11 from the launch pad 41, the assembly `41, 11, 21, 31 is turned to a vertically upright position as shown in FIG. l, and valve 53 is released to release the pressure within chamber 45. The pressure within chamber 14 of first stage 11 will then cause the fiexible bulb connector-seal to laterally collapse and be ejected from the opening 15a, 15b, 15C and liftoff will occur with the subsequent continuing discharge of liquid through metering orifice 15b. The rocket assembly will continue upward under the reaction force infiuence of the ejected water mass from orifice 15b until the pressure in chamber 14 drops sufficiently to enable the then greater pressure within chamber 24 (which was initially approxi- 'mately similar to that of adjacent chambers 14 and 34), to overcome the holding action of bulb connector-seal 27 in openings 25a, 25b, 25e. Upon reaching this pressure difference the 'second and third section assembly will then separate from the first stage in a manner similar to that of first stage 11 and launch pad 41. The second and third stage assembly 21, 311 will continue upward together until a similar pressure differential separation occurs between these two stages, and the third stage will thereupon continue upward alone under its own reaction motor thrust power through liquid ejection from metering orifice 35b. Upon exhaustion of the liquid from each of the stages the thrust will quickly drop to zero and the stage will thereafter drop to the launch area. Upon recovery of all stages the rocket 11 may be reassembled together with launch pad 41 and launched again.

For ease of manufacturing the various stages and the launcher may take various forms. For instance as shown in FIG. 2, illustrating a modified construction of rocket stage section 111, the body 111 may be formed in several pieces which are then suitably bonded together to form the unitary body. In this modified embodiment the rear end wall is formed separately from the side and forward Wall sections 113, 116, as is the self-sealing valve 118 and the bulb connector-seal 117. The rear end wall is formed as two or more split laterally mating sections 115', 115, each having a concavo-concave intermediate groove surface 115a, small diameter concavo-convex metering orifice surface 11511 and reduced diameter neck rim surface 1:15a. With this construction the separately formed pieces may be formed of different materials consistent with their required function. For instance, the bulb connectorseal 117 may be formed of softer more elastic material than body 113, as may self-sealing valve 118. Bulb connector-seal 118 is secured to the main body 113 through bonding of an intermediate neck portion 117e and flange retaining portion .117d to the adjoining area surrounding opening 116 in end wall 11-6. Valve 1181, which is preferably of soft pliant rubber, is inserted through an opening in side wall 113 and is bonded thereto and/or held in place by tight friction `fit which aids in assuring self-sealing of the opening 118a. In addition it may be noted that each of the valve openings 1:18a, 18a, etc. of the various valves may be formed by puncturing with a sharp small diameter needle, or by other conventionally practiced self-closing valve construction tech niques. Further, various other valve constructions may be employed for the valves 118; 18a, etc., as desired, it being desirable however that the valves be self-closing in the discharge direction.

FIG. 3 illustrates a modified launch pad arrangement which provides added simulated realism to the launching operation. In this modified embodiment the housing 243 for the pressurizable fluid chamber 245 of the launch pad 241 has radially extending liquid discharge orifices 244 formed at circumferentially spaced positions about the annular periphery thereof. The orifices 244 preferably have a flared inner seat end and are releasably closed by substantially complementary pressure releasable plugs 242, each having a double tapered retention nodule end 242a seating on seat 244a. The plugs 242 are preferably additionally connected for safety and retention purposes to the launch pad 241 through the medium of a liexible cord or other flexible line 2811 secured through spaced eyes 2157 formed in the annular outer upstanding rim 253.

The launch pad 241 may be secured to the ground for stability, if desired, as with anchor pins 283 extending through the base 251 thereof. While not shown, a tool receiving opening and a removable plug may be provided in the bottom 251 of launch pad 241 as in FIG. 1 if so desired, it being preferred in such cases that the removable tool assistance plug be constructed and shaped for substantially more difiicult removal than the plugs 242 so as to prevent undesired removal of the plugs during operation of the launch pad 241.

A female water hose connection is provided in the wall 243 as indicated at 248 for supply of water to and pressurizing of the chamber 245. Annulus wall 253 has an upwardly concavely curved surface 255 in the path of discharge from the orifices 244 and this surface 255 serves to deflect and disperse water from the orifices 244 upwardly.

In operation of the embodiment of FIG. 3, a rocket 211 partially filled with water is connected to launch pad 241 through insertion of bulb connector-seal 247 in the associated rear discharge and connection opening of the rocket body. Water is then added to chamber 245 through a hose (not shown) connected to hose connector 248 suflicient to pressurize the bulb 247 to operational sealing and holding condition, but insufiicient to effect discharge of said plugs 242 from their orifices 244. The rocket 211 is then pressurized through its associated valve 21311, whereupon the water pressure is increased within chamber 245 by remote control from a conventional water faucet supply connection (not shown) to effect discharge of the plugs 242 and resulting spraying of water through the orifices 244. The radial jets of water will be deflected and dispersed upwardly in a generally ring-shaped pattern, the continuity of which is dependent to a degree upon the number and spacing of orices 244. With a sufficient quantity and size of orifices in comparison to the available water flow rate into chamber 245 the resulting pressure drop will be sufficient to enable launching of rocket 211. However, launching can be assured by turning the faucet full open to eject the plugs 242 and effect the desired water spray action, and thereupon turning off the faucet, as the pressure in the chamber 245 will in the nal condition be reduced to zero, assuring release and lift-off of the rocket 211 from launch pad 241.

In FIGS. 4 and 5 are shown two permissible, though to some degree less advantageous, modifications of rst stage sections of a multistage rocket according to the invention. In each instance the stage section incorporates a pressurizable flexible bulb connector-seal 317 for connection of two adjoining first and second stages 311 and 321, the bulb connector-seal 317 being of tear-drop shape for ease of insertion and relatively greater resistance to removal. This faucet is considered desirable in various instances for all stage bulb connector-seals, the somewhat less advantageous construction lying in the alternative constructions for connection to the launcher. In FIG. 4 the launcher connection is a flanged nozzle 315]c formed on rear wall 315 and having a fluid discharge orifice 315b. With this construction the rocket 311 may be launched with the aid of a mechanical slide release launcher such as shown on Pat. 2,732,657. The discharge orifice 415b in the embodiment of FIG. 5 has a shallow small diameter annular groove 415b formed in the discharge orifice 415b and is adapted to be launched with the aid of a nodular stemmed launcher as provided in U.S. Pat. 3,046,694. Various other hybrid stage sections may be employed as desired, though such are generally considered less desirable than the arrangement in which all stages and the launch pad are connected and separated in a similar manner.

A modified bulb connector-seal 517 is shown in the rocket section embodiment 511 of FIGS. 6-8, wherein the bulb wall 517b has a tear-drop shape for relative ease of insertion in comparison to removal of the bulb connector-seal from its complementary female opening, and in which the bulb is longitudinally reinforced while providing collapsibly lateral flexibility of the wall 51712. This is effected by a longitudinal reinforcing rib unit having ribs 517d integrally connecting, or secured to, the tip and root end portions of bulb connector-seal 517 while being in disconnection therefrom in the intermediate enlarged girth flexible annular wall portion 517b.

FIG. 9 shows a further modified form of flexible bulb connector-seal 617 having a generally squat shape with a relatively large diameter securing rim annulus portion 617b' compared to the depth thereof and a relatively flattened flexible outer end surface 617b. The opening in Wall 616 of rocket stage section 611 is relatively large so as to enable downwardly and inwardly rolling deflection and release of the retaining rini annulus portion 617b' from its complementary retention groove in response to decrease in pressure in the connecting liquid storage chamber of stage section 611. In this embodiment, as in FIG. 2, the bulb connector-seal 617 is formed separately from the main body of the associated rocket stage section 611, and is bonded thereto along retaining flange 617d and intermediate reduced diameter portion 617C, a1- though in some instances it may be suflicient to bond only along flange 61741, in which latter instance the downwardly and inwardly rolling action of the bulb diaphragm connector-seal 617 may extend over a greater distance during stage separation.

That which is claimed is: 1. A toy arrangement comprising a self-propellable missile stage having a pressurizable fluid chamber and a fluid discharge propulsion orifice for said chamber, and a non-self-propelled ground engageable launching base having a lluid-pressure-responsive male connection engageable in releasable holding relation within the fluid expulsion orifice of said self-propellable stage,

said launching base male connection comprising a pressure responsive laterally flexible diaphragm wall section having its interior releasably pressurizable when in stage-connected condition prior to launching and being engageable in male-female holding and sealing relation within a portion of said fluid expulsion orifice of said adjoining stage, and internal depressurization of said laterally flexible diaphragm wall section enabling stage separation therefrom, and

pressure releasing means for said launching base connection to release said adjoining stage, comprising a fluid pressure release valve remote from said base and a conduit in fluid connection between the interior of said pressure responsive laterally flexible diaphragm wall section and said fluid release Valve.

2. A fluid pressure propulsion toy arrangement comprising a fluid pressure propellable body with a pressurizable fluid storage chamber therein and a fluid expulsion orifice in fluid connection between said storage chamber and the outside atmosphere, and a launching base for said propellable body and having a fluid-pressure-responsive flexible inflatably laterally distensible male connector formed thereon and in releasable holding connection with said propellable body through engagement within said fluid expulsion orifice, the interior of said flexible inflatably laterally distensible male connector being releasably pressurizable when in position within said fluid orifice to afford pressure responsively releasable holding engagement therewith.

3. An arrangement according to claim 2, and pressure releasing means for said launching base male connector comprising a fluid pressure release valve remote from said base, and a conduit in fluid connection between the interior of said inllatably laterally distensible male connector and said fluid release valve.

4. A reaction propulsion toy comprising a first body having a pressurizable fluid chamber and a clOSable fluid discharge orifice in fluid connection between said chamber and the outside atmosphere, said body having an internalpressure-responsive laterally flexibly movable male connector diaphragm wall section spaced from said fluid discharge orifice for releasable connection to a second separable body as a function of internal pressure in said body chamber, a second separable body having a female connection releasably engageable in retained relation with said first body by removable insertion of said flexibly movable wall section within said female connection and pressure responsive releasable frictional retentional gripping action on said female connection by said movable wall section, and said second body having means enabling said second body to be propelled away from its held position by said first body flexibly movable wall section upon release therefrom.

5. A reaction propulsion toy according to claim 4, said o o internal-pressure-responsive laterally flexibly movable wall section forming an annular male nose-end connection on said first body.

6. A reaction propulsion toy according to claim 5, said pressure-responsive laterally flexibly movable wall section having a greater pressurized -condition girth intermediate its root and tip ends than adjacent its root end.

7. A fluid pressure propulsion ytoy according to claim 5, said pressure-responsive laterally flexibly movable wall section having a relatively smaller protrudingrelatively rigid tip and engageable Within a further reduced diameter portion of said female connection on said second separable body, said second'body having a pressurizable fluid chamber and a fluid discharge orifice therefor and forming said female connection.

8. A toy according to claim 5, said annulary male noseend connection on said first body having longitudinal bracing extending along its said pressure-responsively laterally flexibly movable wall section, and means effectively connecting said flexibly movable wall section' in longitudinally braced relation to said longitudinal bracing at spaced positions and with disconnection therebetween to thereby enable said flexibly movable wall section to be radially flexed under differential radial pressure thereon.

9. A toy according to claim 8, said bracing extending between the forward end portion of said flexibly movable wall section of said first b ody and a portion of said first body spaced rearwardly from said forward end portion, said inflatably flexibly movable wall section being laterally movable in-and-out relative to said bracing intermediate its root and tip ends, and said bracing having at least one fluid passageway therein connecting between said inllatably flexibly movable wall section and said pressurizable fluid chamber.

10. A reaction propulsion toy according to claim 4, said laterally flexibly movable wall section being annular and being a separate non-integral attachment to the remainder of said first body and means securing said laterally flexibly movable Wall section to the adjoining portion of said first body.

11. A reaction propulsion toy according to claim 4, said male connector diaphragm wall section being bulbous and forming a laterally inflatable flexible nose section engageable within said female connection on said second body.

Y 12. A multistage toy projectile arrangement comprising first and second separable self-propellable bodies each having a fluid discharge orifice, and an inflatable pressureresponsive laterally flexible diaphragm connecting element on one of said :bodies and engageable in pressureresponsive direct gripping and securing and dischargeorifice-sealing relation with the other of said bodies through pressure-responsive securing engagement of said diaphragm connecting element within said fluid discharge orifice of said other of said bodies.

13. A reaction propulsion toy arrangement according to claim 4, said second separable body having a pressurizable chamber and a fluid discharge orifice, said first body movable wall section engaging in fluid-pressure-responsive direct frictional retention gripping and dischargeorifice-sealing relation within said fluid discharge orifice of said first body.

14. A fluid expulsion reaction propulsion toy according to claim 18, said annular flexible diaphragm section being a flexible bulb unit closed'at one end and having a laterally out-turned end flange at its opposite end and forming said end shoulder, saidpmain body section having a laterally inwardly extending portion spaced from said liquid discharge opening and having a connection opening therein, said bulb unit extending through said connection opening and said flange being secured against'v the inner face of said laterally inwardly extending portion about said connection opening.

15. A toy arrangement according to claim 12, said fluid expulsion orifice in said other body having an inner annular surface of varying girth along its length and releasably engaged within and along said s urface of varying girth by said inflatable laterally flexible diaphragm connecting element.

16. A single stage jet-fluid-discharge-propellable first unit for use with another similar unit to be releasably carried thereby and having a fluid carrying and fluid pressurizable body with a combined fluid discharge orifice and female interstage connection, said first unit comprising a first jet fluid discharge propellable body having a pressurizable fluid chamber and a closable fluid discharge orice in fluid connection [between said chamber and the outside atmosphere, said body having a male connector with an internally pressure-responsive flexibly movable diaphragm wall section spaced from said fluid discharge orifice for fluid-pressure-responsive releasable male-female connection to and within said other unit fluid discharge orifice and female interstage connection, said fluid discharge orifice of said first body having a configuration generally complementary to a pressurized condition configuration of said flexibly movable diaphragm wall section of said first body male connector, when disposed in a second fluid discharge orifice similar to said first body discharge orice and which is formed in another fluiddischarge-propelled unit body, whereby multiple interfitting nose-to-orilice stages may be formed with multiples of this body.

17. A fluid expulsion reaction propulsion toy comprising a relatively rigid main body section having a nose end, a central pressurizable liquid-holding chamber and a selfpropulsion liquid discharge opening formed in said main body section for fluid connection between said chamber and the outside atmosphere, said nose end having a relatively thin-walled flexibly movable annular flexible diaphragm connector section in fluid pressure connection with said liquid holding chamber, said annular flexible diaphragm section being a separately formed element of relatively substantially greater flexiblity than said main body section and being secured to said main body section on said nose end thereof, and longitudinal bracing extending within said annular flexible diaphragm section, said annular flexible diaphragm section being effectively connected to said longitudinal bracing in longitudinally braced relation at spaced longitudinal positions adjacent the opposite longitudinal effective ends of said annular flexible diaphragm section and being in longitudinally braced yet laterally flexibly movable relationship with respect to said bracing therewithin.

18. A fluid expulsion reaction propulsion toy according to claim 17, said annular flexible diaphragm section having an annular connecting shoulder portion formed at and about an open inner end thereof, and means forming a sealed connection between said flexible diaphragm and said main body section and including said annular open end connecting shoulder portion.

19. A fluid pressure propulsion toy arrangement cornprising a fluid pressure propellable body with a pressurizable fluid storage chamber therein and a fluid expulsion orifice in fluid connection between said storage chamber and the outside atmosphere, and a launching base for said body and having a differential-fluid-pressure-responsively laterally flexible connector formed thereon and in releasable holding connection with said body through engagement Iwithin said fluid expulsion orifice, the interior of said laterally flexible connector being releasably pressurizable when in position within said fluid expulsion orifice to afford pressure responsively releasable holding engagement therewith.

20. A fluid pressure propulsion toy arrangement comprising a fluid-pressure-propellable body with a pressurizable fluid storage chamber therein and a fluid expulsion orifice in fluid connection between said storage chamber and the otuside atmosphere, and a releasable fluid expulsion orifice-closure unit on another separate body for said orifice and having a male connector with a differential fluid-pressure-responsively laterally flexible diaphragm wall formed thereon and for releasable male-female holding connection with said body through male engagement within a portion of said fluid expulsion orifice, the interior of said laterally flexible diaphragm being releasably pressurizable when in position within said fluid expulsion orifice to afford pressure responsively releasable holding engagement therewith.

21. A toy arrangement according to claim 20 said inflatably flexible connector having a generally circumferentially convex medially distended inflated configuration in fluid pressurized condition and engaged within said fluid expulsion orifice.

22. A toy arrangement according to claim 20, said fluid expulsion orifice having a first inner surface with a first diameter and further inner surfaces forward and rear- 'ward of and adjoining said first diameter inner surface and each having a smaller inner diameter than said first inner surface, said closure unit having its said laterally flexible diaphragm wall gripping male connector engageable in pressure responsively effectively substantially cornplenmenting gripping relation within said differently diametered inner surfaces of said fluid expulsion orifice, to thereby aid in gripping retention by said releasable orifice closure unit male connector within said orifice inner surface.

23. A toy arrangement according to claim 20, said fluid propulsion orice in said fluid-pressure-propellable body being formed by a substantially rigid annular wall section of said body and being thereby directionally stable during fluid expulsion therefrom while also enabling ease of insertion and connection of said laterally flexible diaphragm wall male connector therewithin.

24. For use in launching a propelled toy missile body, a ground-supportable launcher having a pressurizable fluid chamber formed therein and in fluid-pressure-transmitting connection with a fluid-pressure-responsive releasable retaining connection for releasable retaining said missile body, and means for releasing the pressure within said chamber to thereby release the retention of said missile body by said fluid-pressure-responsive releasable retaining connection, said fluid-pressure-responsive retaining connection comprising a male connector having a flexibly laterally movable inflatable diaphragm wall section releasably engaging with the fluid discharge propulsion orifice in said missile body.

25. A fluid-pressure-responsive toy arrangement for use with a separable fluid-pressure-propellable body having a pressurizable fluid storage chamber therein and a fluid expulsion orifice in fluid connection `between said storage chamber and the outside atmosphere, said arrangement comprising a separate holding and releasing body for releasable retentive holding connection to and release from said fluid-pressure-propellable body by differential-fluidpressure-responsive connection to and differential-fluidpressure-responsively assisted discharge from said fluid expulsion orifice, said separate holding and releasing body having a male connector with a fluid-pressure-responsive flexible laterally movable diaphragm wall section for pressure-responsively releasable retentive holding connection with said fluid-pressure-propellable body through engagement thereof within said fluid expulsion orifice of said fluid-pressure-propellable body, the interior of said flexible laterally movable diaphragm wall section being releasably pressurizable when in position within said fluid expulsion orice to afford pressure-responsive releasable holding engagement therewith, said male connector being releasable and expellable from said fluid expulsion orifice as a function of internal depressurization of said male connector when in position within said fluid expulsion orifice to thereby enable separation and self-propulsion of said fluid-pressure propellable body through fluid expulsion from said fluid expulsion orifice thereof.

26. A toy arrangement according to claim 25, said separate holding and releasing body being a non-selfpropelled ground-engageable launching base for said fluid pressure propellable body.

27. A toy arrangement according to claim 2S, said separate body being a uid-pressure-propellable body with a pressurizable uid storage chamber therein and a fluid expulsion propulsion orice therefor which is open during and to enable pressurized uid expulsion propulsion of said separate uid-pressure-propellable body.

28. A toy arrangement according to Claim 25, said flexible laterally movable diaphragm wall section being an annular pressurizably elastically distensible diaphragm element.

References Cited UNITED STATES PATENTS Deterding 46-75 Dragich 46-74 Chupa 273-58(3) DeSee et al. 273-58(3)X Holderer 46-74(C) .Toffe 46-74'(C) Ryan 46-74(C) Lungren 206-(Inflatab1e) LOUIS G. MANCENE, Primary Examiner R. F. CUTTING, Assistant Examiner 

